Method for the operation of a gas turbo group
View Patent ↗A method for operating a gas turbine set comprises the compression of an air mass flow in a compressor, feeding the compressed air mass flow into a first combustion chamber, burning the first mass fuel flow in the first combustion chamber in the compressed mass air flow, expanding the resulting hot gas in the first turbine, feeding the partially expanded hot gas into a second combustion chamber, and burning a second mass fuel flow in the second combustion chamber in the partially expanded hot gas. The method furthermore comprises supplying to the gas turbine set the first mass fuel flow and the second mass fuel flow preferably in a common supply line with a fuel supply pressure, and stipulating division of the total mass flow into a first and second mass fuel flow according to a normal operation concept. When the boundary value of the fuel supply pressure for example in the preferably common supply line is not reached, there is a deviation from the division according to the normal operating concept. Relative to the normal operation concept the first mass fuel flow is reduced by the difference mass flow and the second mass fuel flow is increased at least by the difference mass flow.
1. Method for operating a gas turbine set, comprising:
compression of an air mass flow in a compressor,
feeding the compressed air mass flow into a first combustion chamber,
burning a first mass fuel flow in the first combustion chamber in the compressed air mass flow,
expanding resulting hot gas in a first turbine,
feeding partially expanded hot gas into a second combustion chamber,
burning a second mass fuel flow in a second combustion chamber in the partially expanded hot gas,
supplying to the gas turbine set the first mass fuel flow and the second mass fuel flow with a fuel supply pressure, and
dividing the total mass flow into the first and second mass fuel flows according to a normal operation mode, wherein when a limit value of fuel supply pressure is not reached, deviating from the division according to the normal operation mode such that the first mass fuel flow is reduced by a difference mass flow and the second mass fuel flow is increased at least by the difference mass flow.
2. Method as claimed in claim 1 , wherein the method furthermore comprises supplying to the gas turbine set the first mass fuel flow and the second mass fuel flow in a common supply line with a fuel supply pressure, when the limit value of the fuel supply pressure in the common supply line is not reached there being a deviation from the division according to the normal operation mode, and relative to the normal operation mode reducing the first fuel mass flow by the difference mass flow, and increasing the second mass fuel flow by at least the difference mass flow.
3. Method as claimed in claim 1 , wherein the normal operation mode comprises dividing the total mass flow as a function of the delivery of useful output power (P cur ) of the gas turbine set.
4. Method as claimed in claim 1 , comprising determining the entry temperature of the hot gas upon entry into the first turbine for dividing the total mass flow, metering the first mass fuel flow to the first combustion chamber such that the entry temperature reaches an allowable upper limit value, and metering the portion of the total mass flow in excess to the second combustion chamber as a second mass fuel flow.
5. Method as claimed in claim 1 , comprising setting the total mass flow such that the delivery of useful output power of the gas turbine set corresponds to a setpoint.
6. Method as claimed in claim 1 , comprising establishment of the limit value of the fuel supply pressure depending on the delivery of useful output power of the gas turbine set.
7. Method as claimed in claim 1 , comprising directly measuring the fuel supply pressure.
8. Method as claimed in claim 1 , comprising fixing the difference mass flow depending on the difference between the pressure limit value and an actual supply pressure, the difference mass flow being greater, the smaller the effective supply pressure.
9. Method as claimed in claim 1 , comprising matching internal fuel distribution of the first combustion chamber depending on a change of the first mass fuel flow.
10. Method as claimed in claim 1 , comprising keeping the total mass flow constant, reducing the first mass fuel flow by the difference mass flow, and increasing the second mass fuel flow by the difference mass flow.
11. Method as claimed in claim 1 , comprising reducing the first mass fuel flow by the difference mass flow, increasing the second mass fuel flow by the difference mass flow, and increasing the second mass fuel flow by another mass flow such that the delivery of useful output power of the gas turbine set is kept constant.
12. Method as claimed in claim 1 , comprising increasing the delivery of useful output power of the gas turbine set, increasing the total mass flow, dividing the total mass flow according to the normal operation mode between the first mass fuel flow and the second mass fuel flow, and when the limit value of the fuel supply pressure is not reached, not continuing to raise the first mass fuel flow, and metering the increase of the total mass flow which is necessary to increase the delivery of useful output power to the full extent to the second mass fuel flow.
13. Method as claimed in claim 9 , comprising reducing the first mass fuel flow by the difference mass flow, increasing the second mass fuel flow by the difference mass flow, and increasing the second mass fuel flow by another mass flow such that the delivery of useful output power of the gas turbine set is kept constant.
14. Method as claimed in claim 9 , comprising increasing the delivery of useful output power of the gas turbine set, increasing the total mass flow, dividing the total mass flow according to the normal operation mode between the first mass fuel flow and the second mass fuel flow, and when the limit value of the fuel supply pressure is not reached, not continuing to raise the first mass fuel flow, and metering the increase of the total mass flow which is necessary to increase the delivery of useful output power to the full extent to the second mass fuel flow.